CN114165360A - Method and device for adjusting thrust of liquid rocket - Google Patents
Method and device for adjusting thrust of liquid rocket Download PDFInfo
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- CN114165360A CN114165360A CN202111585983.6A CN202111585983A CN114165360A CN 114165360 A CN114165360 A CN 114165360A CN 202111585983 A CN202111585983 A CN 202111585983A CN 114165360 A CN114165360 A CN 114165360A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
An embodiment of the present application provides a method for adjusting thrust of a liquid rocket, the method including: acquiring actual operation parameters of the liquid rocket, wherein the actual operation parameters are used for representing the actual operation condition inside the liquid rocket; acquiring target operation parameters corresponding to the actual operation parameters; determining a target fuel flow or a target oxygen flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters; and adjusting the opening of a fuel regulating valve according to the target fuel flow, or adjusting the opening of an oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of an oxygen main regulating valve according to the target oxygen flow resistance. The liquid rocket thrust can be accurately controlled and adjusted at least to a certain extent, the controllability of the liquid rocket is improved, and the application development of the liquid rocket technology is promoted.
Description
Technical Field
The application relates to the technical field of control of liquid rockets, in particular to a method and a device for adjusting thrust of a liquid rocket.
Background
With the rapid development of commercial carrier rockets, the cost of the rockets is reduced, and the reduction of the launching cost of the carrier rockets is a technical problem mainly considered by the design of the commercial carrier rockets. The return launch vehicle is one of the low cost design directions for current launch vehicles. The liquid rocket thrust adjusting technology is one of the key technologies for designing the return carrier rocket, but the liquid rocket thrust adjusting technology is not disclosed by related information at home and abroad.
Therefore, a thrust adjusting method for a liquid rocket is urgently needed by the technical personnel in the field to accurately control and adjust the thrust of the liquid rocket, improve the controllability of the liquid rocket and promote the application and development of the liquid rocket.
Disclosure of Invention
The embodiment of the application provides a method and a device for adjusting the thrust of a liquid rocket, which can accurately control and adjust the thrust of the liquid rocket at least to a certain extent, improve the controllability of the liquid rocket and promote the application and development of the liquid rocket technology.
Other features and advantages of the present application will be apparent from the following detailed description, or may be learned by practice of the application.
According to one aspect of the present application, there is provided a method of adjusting thrust of a liquid rocket, the method comprising: acquiring actual operation parameters of the liquid rocket, wherein the actual operation parameters are used for representing the actual operation condition inside the liquid rocket; acquiring target operation parameters corresponding to the actual operation parameters; determining a target fuel flow or a target oxygen flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters; and adjusting the opening of a fuel regulating valve according to the target fuel flow, or adjusting the opening of an oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of an oxygen main regulating valve according to the target oxygen flow resistance.
In some embodiments of the present application, the liquid rocket includes a turbocharger device and a thrust chamber, and the operating parameters of the liquid rocket include a turbine inlet temperature of the turbocharger device, an oxygen pump flow of the turbocharger device, a fuel pump flow of the turbocharger device, and a thrust chamber pressure of the thrust chamber.
In some embodiments of the present application, determining a target fuel flow rate of the liquid rocket based on the target operating parameter and the actual operating parameter by a PI control method includes: calculating a pressure difference of the thrust chamber based on a target thrust chamber pressure and an actual thrust chamber pressure; based on the pressure difference, a target fuel flow rate into the turbocharger device is calculated by a PI control method.
In some embodiments of the present application, the adjusting the opening of the fuel regulating valve according to the target fuel flow rate includes: acquiring a first relation table of the opening of a fuel regulating valve and the fuel flow, wherein the first relation table records the corresponding relation between the opening of each fuel regulating valve and the fuel flow passing through the fuel regulating valve; determining a target fuel regulating valve opening corresponding to the target fuel flow through the first relation table; adjusting the opening degree of the fuel regulating valve to the target fuel regulating valve opening degree.
In some embodiments of the present application, determining a target oxygen flow rate of the liquid rocket through a PI control method based on the target operating parameter and the actual operating parameter comprises: calculating a turbine inlet temperature difference based on the target turbine inlet temperature and the actual turbine inlet temperature; calculating a first target mixture ratio of fuel to oxygen of the turbocharger device by a PI control method based on the temperature difference; a target fuel flow rate into the turbocharger device is obtained, and a target oxygen side-flow rate into the turbocharger device is calculated based on the first target mixing ratio and the target fuel flow rate.
In some embodiments of the present application, the adjusting the opening of the oxygen secondary regulator valve according to the target oxygen flow rate includes: acquiring a second relation table of the opening degree of the oxygen auxiliary regulating valve and the oxygen flow, wherein the second relation table records the corresponding relation between the opening degree of each oxygen auxiliary regulating valve and the oxygen flow passing through the regulating valve; determining a target oxygen secondary regulating valve opening corresponding to the target oxygen secondary flow through the second relation table; and adjusting the opening degree of the oxygen auxiliary regulating valve to the target opening degree of the oxygen auxiliary regulating valve.
In some embodiments of the present application, obtaining a target oxygen pump flow rate corresponding to the actual oxygen pump flow rate comprises: acquiring an actual fuel pump flow; acquiring a second target mixing ratio of fuel and oxygen of the thrust chamber; the target oxygen pump flow rate is calculated based on the actual fuel pump flow rate and a second target mixture ratio.
In some embodiments of the present application, the liquid rocket further comprises an oxygen main conduit for transporting oxygen into the thrust chamber; determining a target oxygen main flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters, and the method comprises the following steps: calculating a difference in a main flow rate of oxygen entering the thrust chamber based on a target oxygen pump flow rate and an actual oxygen pump flow rate; and determining a target oxygen main flow resistance of an oxygen main duct of the liquid rocket through a PI control method based on the oxygen main flow difference.
In some embodiments of the present application, the adjusting the opening of the main oxygen regulating valve according to the target oxygen flow resistance comprises: acquiring a third relation table of the opening of the main oxygen regulating valve and the oxygen flow resistance, wherein the third relation table comprises a corresponding relation of the opening of the main oxygen regulating valve and the oxygen flow resistance of the main oxygen guide pipe; determining a target oxygen main regulating valve opening corresponding to the target oxygen main flow resistance through the third relation table; and adjusting the opening degree of the main oxygen regulating valve to the target opening degree of the main oxygen regulating valve.
According to one aspect of the present application, there is provided a liquid rocket thrust adjustment device, the device comprising: the liquid rocket control system comprises a first acquisition unit, a second acquisition unit and a control unit, wherein the first acquisition unit is used for acquiring actual operation parameters of the liquid rocket, and the actual operation parameters are used for representing actual operation conditions inside the liquid rocket; a second acquisition unit configured to acquire a target operation parameter corresponding to the actual operation parameter; a determination unit for determining a target fuel flow rate or a target oxygen flow resistance of the liquid rocket by a PI control method based on the target operation parameter and the actual operation parameter; and the adjusting unit is used for adjusting the opening of the fuel regulating valve according to the target fuel flow, or adjusting the opening of the oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of the oxygen main regulating valve according to the target oxygen resistance.
Based on the scheme, the application has at least the following advantages or progress effects:
the method and the device can realize control and regulation aiming at the thrust of the liquid rocket by monitoring the deviation between the actual operating parameters and the target operating parameters of the liquid rocket, determining the target fuel flow or the target oxygen flow resistance through a PI control method, and then correspondingly regulating the opening of each regulating valve. In addition, the target fuel flow or the target oxygen flow resistance of the liquid rocket is determined through a PI control method, and the accuracy of adjusting the thrust of the liquid rocket can be improved.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present application and together with the description, serve to explain the principles of the application. It is obvious that the drawings in the following description are only some embodiments of the application, and that for a person skilled in the art, other drawings can be derived from them without inventive effort. In the drawings:
FIG. 1 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 2 shows a partial schematic structural view of a liquid rocket in one embodiment of the present application;
FIG. 3 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 4 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 5 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 6 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 7 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 8 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 9 shows a flow diagram of a method of regulating liquid rocket thrust in one embodiment of the present application;
FIG. 10 shows a schematic view of a liquid rocket thrust modulation device in an embodiment of the present application;
FIG. 11 illustrates a schematic diagram of a computer system suitable for use in implementing embodiments of the present application.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art.
Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of embodiments of the application. One skilled in the relevant art will recognize, however, that the subject matter of the present application can be practiced without one or more of the specific details, or with other methods, components, devices, steps, and so forth. In other instances, well-known methods, devices, implementations, or operations have not been shown or described in detail to avoid obscuring aspects of the application.
The block diagrams shown in the figures are functional entities only and do not necessarily correspond to physically separate entities. I.e. these functional entities may be implemented in the form of software, or in one or more hardware modules or integrated circuits, or in different networks and/or processor means and/or microcontroller means.
The flow charts shown in the drawings are merely illustrative and do not necessarily include all of the contents and operations/steps, nor do they necessarily have to be performed in the order described. For example, some operations/steps may be decomposed, and some operations/steps may be combined or partially combined, so that the actual execution sequence may be changed according to the actual situation.
It is noted that the terms first, second and the like in the description and claims of the present application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the objects so used are interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in other sequences than those illustrated or described herein.
Referring to fig. 1, fig. 1 shows a simplified flow diagram of a method for adjusting thrust of a liquid rocket in one embodiment of the present application, which may include steps S101-S104:
step S101, obtaining actual operation parameters of the liquid rocket, wherein the actual operation parameters are used for representing the actual operation condition inside the liquid rocket.
And step S102, acquiring target operation parameters corresponding to the actual operation parameters.
And S103, determining the target fuel flow or the target oxygen flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters.
And step S104, adjusting the opening of the fuel regulating valve according to the target fuel flow, or adjusting the opening of the oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of the oxygen main regulating valve according to the target oxygen resistance.
In the application, the thrust of the liquid rocket can be quickly and accurately adjusted by monitoring the deviation between the actual operating parameters and the target operating parameters of the liquid rocket, determining the target fuel flow or the target oxygen flow resistance through a PI control method, and then correspondingly adjusting each adjusting valve.
Referring to fig. 2, fig. 2 shows a partial schematic structural diagram of a liquid rocket in an embodiment of the present application, in which the liquid rocket may include a turbocharger 205 and a thrust chamber 208, and the operating parameters of the liquid rocket may include a turbine inlet temperature of the turbocharger 205, an oxygen pump flow of the turbocharger 205, a fuel pump flow of the turbocharger 205, and a thrust chamber pressure of the thrust chamber 208.
In this application, when the engine is in operation, after the fuel entering the thrust chamber 208 from the fuel tank 202 is pressurized by the fuel pump 204 of the turbocharger 205, most of the fuel enters the thrust chamber 208 to be combusted, and another part of the fuel enters the gas generator 210 of the turbocharger 205 through the fuel regulating valve 206. After the liquid oxygen entering the thrust chamber 208 from the oxygen storage tank 201 is pressurized by the oxygen pump 203 of the turbo-charging device 205, most of the liquid oxygen enters the thrust chamber 208 through the oxygen main regulating valve 207 for combustion, and a part of the liquid oxygen enters the fuel gas generator 210 of the turbo-charging device 205 through the oxygen auxiliary regulating valve 209; after the fuel and oxygen entering the gas generator 210 are combusted, high-temperature gas is generated to drive the turbine of the turbocharger 205 to rotate and do work, so that the fuel and oxygen are pressurized.
Based on the scheme, the power part of the liquid rocket can be provided with the turbocharging device, so that the air inflow of the thrust chamber is improved. Because the air inlet efficiency is increased, the fuel is more fully combusted, and the power part of the liquid rocket outputs higher power.
Referring to fig. 3, fig. 3 is a simplified flow chart of a method for adjusting thrust of a liquid rocket according to an embodiment of the present application, where determining a target fuel flow rate of the liquid rocket through a PI control method based on the target operating parameter and the actual operating parameter may include steps S301 to S302:
in step S301, a pressure difference of the thrust chamber is calculated based on the target thrust chamber pressure and the actual thrust chamber pressure.
Step S302, calculating a target fuel flow rate entering the turbocharger device through a PI control method based on the pressure difference.
In the present application, the target thrust chamber pressure P is used as a function of0Actual thrust chamber pressure P measured with a sensortObtaining a pressure difference Δ P, and performing PI control to calculate a target fuel flow rate entering the turbocharger device using the pressure difference Δ P
The pressure difference Δ P may be calculated by the following equation:
ΔP＝P0-Pt
wherein the pressure difference is Δ P, and the target thrust chamber pressure is P0Said actual thrust chamber pressure is Pt。
In order to reduce the influence of measurement noise, the PI control calculation scheme can cancel a differential calculation link and adopt proportional and integral control, namely PI control. The theoretical parameters designed according to the engine are selected for calculation, and the fuel flow and the actual thrust chamber pressure P can be obtainedtTheoretical mean value of the ratio
The target fuel flow rate entering the turbocharger device can be calculated by PI control according to the following formula
Wherein k is1Can be that
0.3 to 0.6 times of (k)2Can be k10.2 to 0.4 times of the amount of the active ingredient.
Referring to fig. 4, fig. 4 is a simplified flow chart of a method for adjusting thrust of a liquid rocket according to an embodiment of the present application, where the method for adjusting the opening of a fuel regulating valve according to the target fuel flow rate may include steps S401 to S403:
step S401, a first relation table of the opening of the fuel regulating valve and the fuel flow is obtained, and the first relation table records the corresponding relation between the opening of each fuel regulating valve and the fuel flow passing through the fuel regulating valve.
And step S402, determining a target fuel regulating valve opening corresponding to the target fuel flow through the first relation table.
In step S403, the opening degree of the fuel regulating valve is adjusted to the target fuel regulating valve opening degree.
In this application, the first relation table may be preloaded in the liquid rocket, and in practical application, only the first relation table needs to be read, the target fuel regulating valve opening degree is obtained according to the target fuel flow, and the fuel regulating valve is controlled to adjust the opening degree to the target fuel regulating valve opening degree.
For example, the target fuel flow rate is calculated as a, and the first relational table in which the opening degree of the fuel regulating valve corresponding to a is 55% is read. The fuel regulating valve is adjusted from the prior opening degree of 35% to 55% without difficulty.
Referring to fig. 5, fig. 5 is a simplified flow chart of a method for adjusting thrust of a liquid rocket according to an embodiment of the present application, where the method for determining a target oxygen flow rate of the liquid rocket through a PI control method based on the target operating parameter and the actual operating parameter may include steps S501-S503:
in step S501, a temperature difference at the turbine inlet is calculated based on the target turbine inlet temperature and the actual turbine inlet temperature.
Step S502, calculating a first target mixing ratio of fuel and oxygen of the turbocharger device through a PI control method based on the temperature difference.
Step S503 is to acquire a target fuel flow rate entering the turbocharger device, and calculate a target oxygen sub-flow rate entering the turbocharger device based on the first target mixture ratio and the target fuel flow rate.
In the present application, the turbine inlet temperature T is based on a target turbine inlet temperature0Actual turbine inlet temperature T measured with a sensortObtaining a temperature difference Delta T, and performing PI control to calculate a first target mixing ratio r of fuel and oxygen of the turbocharger device by using the temperature difference Delta T1。
The temperature difference Δ T may be calculated by the following formula:
ΔT＝T0-Tt
wherein the temperature difference is Δ T and the target turbine inlet temperature is T0Said actual turbine inlet temperature is Tt。
In order to reduce the influence of measurement noise, the PI control calculation method can cancel a differential calculation link and adopt proportionAnd integral control. Selecting theoretical parameters designed according to the engine for calculation, and obtaining the mixing ratio of fuel and oxygen of the turbocharging device and the actual turbine inlet temperature as TtTheoretical mean value of the ratio
The first target mixture ratio r of fuel to oxygen of the turbocharger device can be calculated by PI control with the following formula1：
r1＝k3×ΔT+k4∫ΔT
Wherein k is3Can be that
0.2 to 0.4 times of (k)4Can be k30.2 to 0.3 times of the amount of the active ingredient.
After the first target mixture ratio is calculated, a target secondary oxygen flow into the turbocharger device may be calculated based on the target fuel flow into the turbocharger device.
The target secondary oxygen flow may be calculated according to the following equation:
wherein the target secondary oxygen flow is
The target fuel flow rate is
The first target mixing ratio is r1。
For example, in the conventional liquid rocket, the first target mixture ratio is B and the target fuel flow rate is B, and the target secondary oxygen flow rate is B/B.
Referring to fig. 6, fig. 6 is a simplified flow chart illustrating a method for adjusting thrust of a liquid rocket according to an embodiment of the present application, where the method for adjusting the opening of the oxygen secondary regulating valve according to the target oxygen flow rate may include steps S601-S603:
step S601 is to obtain a second relationship table of the opening degree of the oxygen auxiliary regulating valve and the oxygen flow rate, where the second relationship table records the correspondence between the opening degree of each oxygen auxiliary regulating valve and the oxygen flow rate passing through the regulating valve.
In step S602, a target opening degree of the auxiliary oxygen regulation valve corresponding to the target auxiliary oxygen flow rate is determined from the second relational table.
And step S603 of adjusting the opening degree of the oxygen auxiliary regulating valve to the target oxygen auxiliary regulating valve opening degree.
In the application, the second relation table is preloaded in the liquid rocket, and in practical application, only the second relation table needs to be read, the target oxygen auxiliary regulating valve opening degree can be obtained according to the target oxygen auxiliary flow, and the target oxygen auxiliary regulating valve opening degree is controlled to be adjusted to the target oxygen auxiliary regulating valve opening degree.
For example, the target fuel flow rate is calculated as C, and the second relation table in which the opening degree of the fuel regulating valve corresponding to C is 43% is read, and the target oxygen auxiliary regulating valve is adjusted from the existing opening degree of 30% to 43% without difficulty.
Referring to fig. 7, fig. 7 is a simplified flow chart of a method for adjusting thrust of a liquid rocket in an embodiment of the present application, where the method for obtaining a target oxygen pump flow rate corresponding to the actual oxygen pump flow rate may include steps S701 to S703:
in step S701, the actual fuel pump flow rate is acquired.
Step S702 acquires a second target mixture ratio of fuel and oxygen of the thrust chamber.
In step S703, the target oxygen pump flow rate is calculated based on the actual fuel pump flow rate and a second target mixture ratio.
In the present application, in order to maintain smooth operation of the liquid rocket, the second target mixture ratio needs to be set according to actual conditions, and thus is not difficult to obtain. In order to keep the ratio of fuel and oxygen entering the thrust chamber as stable as possible, the target oxygen pump flow rate needs to be calculated and set according to the actual fuel pump flow rate, and may be calculated according to the following formula:
wherein the target oxygen pump flow rate is
The actual fuel pump flow rate is
The second target mixing ratio is r2。
For example, in the conventional liquid rocket, the actual fuel pump flow rate is D, and the second target mixing ratio is 0.5, so it is not difficult to calculate the target oxygen pump flow rate to be 2D.
Referring to fig. 8, fig. 8 shows a simplified flow diagram of a method of regulating thrust of a liquid rocket in an embodiment of the present application, the liquid rocket further comprising an oxygen main conduit for delivering oxygen into the thrust chamber; the method of determining the target oxygen main flow resistance of the liquid rocket through the PI control method based on the target operation parameter and the actual operation parameter may include steps S801-S802:
step S801, based on the target oxygen pump flow rate and the actual oxygen pump flow rate, calculates a difference in the main flow rate of oxygen entering the thrust chamber.
Step S802, determining a target oxygen main flow resistance of an oxygen main duct of the liquid rocket through a PI control method based on the oxygen main flow difference.
In the present application, since the delivery resistance of the main oxygen conduit entering the thrust chamber has a large influence on the delivery of oxygen, in order to more accurately adjust or control the thrust of the liquid rocket, it is necessary to determine the target main oxygen regulating valve opening degree according to the flow resistance of the main oxygen conduit.
In the present application, the target oxygen pump flow rate may be relied upon
And the actual oxygen pump flow
Calculating a flow difference
Using flow difference
Performing PI control to calculate the target oxygen main flow resistance Z of the oxygen main duct of the liquid rocket1。
The flow difference can be calculated by the following formula
Wherein the target oxygen pump flow rate is
The actual oxygen pump flow rate is
The flow difference is
In order to reduce the influence of measurement noise, the PI control method cancels a differential calculation link and adopts proportional and integral control. The theoretical average value of the oxygen pump flow and the oxygen main flow resistance can be obtained by selecting and calculating theoretical parameters designed according to the engine
PI control can be carried out by the following formula to calculate the target oxygen main flow resistanceZ1：
Wherein k is5Can be that
0.1 to 0.3 times of (k)6Can be k50.1 to 0.2 times of the amount of the active ingredient.
Referring to fig. 9, fig. 9 is a flow chart illustrating a method of adjusting thrust of a liquid rocket in an embodiment of the present application. The method of adjusting the opening degree of the oxygen main adjusting valve according to the target oxygen flow resistance may include steps S901 to S903:
step S901, a third relation table of the opening of the main oxygen regulating valve and the oxygen flow resistance is obtained, where the third relation table includes a corresponding relation between the opening of the main oxygen regulating valve and the oxygen flow resistance of the main oxygen duct.
Step S902, determining a target oxygen main regulation valve opening degree corresponding to the target oxygen main flow resistance through the third relation table.
And a step S902 of adjusting the opening degree of the oxygen main adjusting valve to the target oxygen main adjusting valve opening degree.
In the application, the third relation table is preloaded in the liquid rocket, and in practical application, the target oxygen main regulating valve opening degree can be obtained by only reading the third relation table and according to the target oxygen main flow resistance, and the target oxygen main regulating valve opening degree is controlled to be adjusted to the target oxygen main regulating valve opening degree.
For example, the target fuel flow rate is calculated as E, the third relation table is read, the second relation table records that the opening degree of the fuel regulating valve corresponding to E is 25%, and the target oxygen auxiliary regulating valve is adjusted from 55% of the existing opening degree to 25%.
Next, an apparatus embodiment of the present application will be described with reference to the drawings.
Referring to FIG. 10, FIG. 10 shows a schematic view of a liquid rocket thrust modulation device in an embodiment of the present application. The liquid rocket thrust adjustment device 1000 may include: a first acquisition unit 1001, a second acquisition unit 1002, a determination unit 1003, and an adjustment unit 1004.
The liquid rocket thrust adjusting device 1000 may be specifically configured as follows: a first obtaining unit 1001, configured to obtain actual operation parameters of a liquid rocket, where the actual operation parameters are used to represent actual operation conditions inside the liquid rocket; a second obtaining unit 1002, configured to obtain a target operation parameter corresponding to the actual operation parameter; a determination unit 1003 used for determining a target fuel flow rate or a target oxygen flow resistance of the liquid rocket by a PI control method based on the target operation parameter and the actual operation parameter; an adjusting unit 1004 is used for adjusting the opening degree of the fuel regulating valve according to the target fuel flow, or adjusting the opening degree of the oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening degree of the oxygen main regulating valve according to the target oxygen resistance.
Referring to FIG. 11, FIG. 11 is a diagram illustrating a computer system suitable for implementing embodiments of the present application.
It should be noted that the computer system 1100 shown in fig. 11 is only an example, and should not bring any limitation to the functions and the scope of the application of the embodiments.
As shown in fig. 11, a computer system 1100 includes a Central Processing Unit (CPU)1101, which can perform various appropriate actions and processes, such as performing the methods described in the above embodiments, according to a program stored in a Read-Only Memory (ROM) 1102 or a program loaded from a storage section 1108 into a Random Access Memory (RAM) 1103. In the RAM 1103, various programs and data necessary for system operation are also stored. The CPU 1101, ROM 1102, and RAM 1103 are connected to each other by a bus 1104. An Input/Output (I/O) interface 1105 is also connected to bus 1104.
The following components are connected to the I/O interface 1105: an input portion 1106 including a keyboard, mouse, and the like; an output section 1107 including a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, a speaker, and the like; a storage section 1108 including a hard disk and the like; and a communication section 1109 including a Network interface card such as a LAN (Local Area Network) card, a modem, or the like. The communication section 1109 performs communication processing via a network such as the internet. A driver 1110 is also connected to the I/O interface 1105 as necessary. A removable medium 1111, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, or the like, is mounted on the drive 1110 as necessary, so that a computer program read out therefrom is mounted into the storage section 1108 as necessary.
In particular, according to embodiments of the application, the processes described above with reference to the flow diagrams may be implemented as computer software programs. For example, embodiments of the present application include a computer program product comprising a computer program embodied on a computer readable medium, the computer program comprising program code for performing the method illustrated by the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network through the communication portion 1109 and/or installed from the removable medium 1111. When the computer program is executed by a Central Processing Unit (CPU)1101, various functions defined in the system of the present application are executed.
It should be noted that the computer readable medium shown in the embodiments of the present application may be a computer readable signal medium or a computer readable storage medium or any combination of the two. A computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples of the computer readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a Read-Only Memory (ROM), an Erasable Programmable Read-Only Memory (EPROM), a flash Memory, an optical fiber, a portable Compact Disc Read-Only Memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the present application, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In this application, however, a computer readable signal medium may include a propagated data signal with computer readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated data signal may take many forms, including, but not limited to, electro-magnetic, optical, or any suitable combination thereof. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wired, etc., or any suitable combination of the foregoing.
The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present application. Each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams or flowchart illustration, and combinations of blocks in the block diagrams or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The units described in the embodiments of the present application may be implemented by software, or may be implemented by hardware, and the described units may also be disposed in a processor. Wherein the names of the elements do not in some way constitute a limitation on the elements themselves.
As another aspect, the present application also provides a computer program product or computer program comprising computer instructions stored in a computer readable storage medium. The processor of the computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions to cause the computer device to execute the method for adjusting the thrust of the liquid rocket described in the above embodiment.
As another aspect, the present application also provides a computer-readable medium, which may be contained in the electronic device described in the above embodiments; or may exist separately without being assembled into the electronic device. The computer-readable medium carries one or more programs which, when executed by the electronic device, cause the electronic device to implement the method for adjusting thrust of a liquid rocket described in the above embodiments.
It should be noted that although in the above detailed description several modules or units of the device for action execution are mentioned, such a division is not mandatory. Indeed, the features and functionality of two or more modules or units described above may be embodied in one module or unit, according to embodiments of the application. Conversely, the features and functions of one module or unit described above may be further divided into embodiments by a plurality of modules or units.
Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein may be implemented by software, or by software in combination with necessary hardware. Therefore, the technical solution according to the embodiments of the present application can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a usb disk, a removable hard disk, etc.) or on a network, and includes several instructions to enable a computing device (which can be a personal computer, a server, a touch terminal, or a network device, etc.) to execute the method according to the embodiments of the present application.
Other embodiments of the present application will be apparent to those skilled in the art from consideration of the specification and practice of the embodiments disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains.
It will be understood that the present application is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the application is limited only by the appended claims.
Claims (10)
1. A method for adjusting thrust of a liquid rocket, the method comprising:
acquiring actual operation parameters of the liquid rocket, wherein the actual operation parameters are used for representing the actual operation condition inside the liquid rocket;
acquiring target operation parameters corresponding to the actual operation parameters;
determining a target fuel flow or a target oxygen flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters;
and adjusting the opening of a fuel regulating valve according to the target fuel flow, or adjusting the opening of an oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of an oxygen main regulating valve according to the target oxygen flow resistance.
2. The method of regulating according to claim 1, wherein the liquid rocket comprises a turbocharger device and a thrust chamber, and the operating parameters of the liquid rocket comprise a turbine inlet temperature of the turbocharger device, an oxygen pump flow of the turbocharger device, a fuel pump flow of the turbocharger device, and a thrust chamber pressure of the thrust chamber.
3. The tuning method of claim 2, wherein determining a target fuel flow rate of the liquid rocket via a PI control method based on the target operating parameter and the actual operating parameter comprises:
calculating a pressure difference of the thrust chamber based on a target thrust chamber pressure and an actual thrust chamber pressure;
based on the pressure difference, a target fuel flow rate into the turbocharger device is calculated by a PI control method.
4. The adjustment method according to claim 3, characterized in that the adjusting of the fuel regulating valve opening degree according to the target fuel flow rate includes:
acquiring a first relation table of the opening of a fuel regulating valve and the fuel flow, wherein the first relation table records the corresponding relation between the opening of each fuel regulating valve and the fuel flow passing through the fuel regulating valve;
determining a target fuel regulating valve opening corresponding to the target fuel flow through the first relation table;
adjusting the opening degree of the fuel regulating valve to the target fuel regulating valve opening degree.
5. The tuning method of claim 2, wherein determining a target oxygen flow rate of the liquid rocket via a PI control method based on the target operating parameter and the actual operating parameter comprises:
calculating a turbine inlet temperature difference based on the target turbine inlet temperature and the actual turbine inlet temperature;
calculating a first target mixture ratio of fuel to oxygen of the turbocharger device by a PI control method based on the temperature difference;
a target fuel flow rate into the turbocharger device is obtained, and a target oxygen side-flow rate into the turbocharger device is calculated based on the first target mixing ratio and the target fuel flow rate.
6. The regulating method according to claim 5, wherein the adjusting of the opening degree of the oxygen secondary regulating valve according to the target oxygen flow rate includes:
acquiring a second relation table of the opening degree of the oxygen auxiliary regulating valve and the oxygen flow, wherein the second relation table records the corresponding relation between the opening degree of each oxygen auxiliary regulating valve and the oxygen flow passing through the regulating valve;
determining a target oxygen secondary regulating valve opening corresponding to the target oxygen secondary flow through the second relation table;
and adjusting the opening degree of the oxygen auxiliary regulating valve to the target opening degree of the oxygen auxiliary regulating valve.
7. The adjustment method according to claim 2, wherein obtaining a target oxygen pump flow rate corresponding to the actual oxygen pump flow rate comprises:
acquiring an actual fuel pump flow;
acquiring a second target mixing ratio of fuel and oxygen of the thrust chamber;
the target oxygen pump flow rate is calculated based on the actual fuel pump flow rate and a second target mixture ratio.
8. The conditioning method of claim 7, wherein the liquid rocket further comprises an oxygen main conduit for conveying oxygen into the thrust chamber; determining a target oxygen main flow resistance of the liquid rocket through a PI control method based on the target operation parameters and the actual operation parameters, and the method comprises the following steps:
calculating a difference in a main flow rate of oxygen entering the thrust chamber based on a target oxygen pump flow rate and an actual oxygen pump flow rate;
and determining a target oxygen main flow resistance of an oxygen main duct of the liquid rocket through a PI control method based on the oxygen main flow difference.
9. The regulating method according to claim 8, wherein the adjusting of the oxygen main regulating valve opening degree according to the target oxygen flow resistance comprises:
acquiring a third relation table of the opening of the main oxygen regulating valve and the oxygen flow resistance, wherein the third relation table comprises a corresponding relation of the opening of the main oxygen regulating valve and the oxygen flow resistance of the main oxygen guide pipe;
determining a target oxygen main regulating valve opening corresponding to the target oxygen main flow resistance through the third relation table;
and adjusting the opening degree of the main oxygen regulating valve to the target opening degree of the main oxygen regulating valve.
10. A liquid rocket thrust modulation device, the device comprising:
the liquid rocket control system comprises a first acquisition unit, a second acquisition unit and a control unit, wherein the first acquisition unit is used for acquiring actual operation parameters of the liquid rocket, and the actual operation parameters are used for representing actual operation conditions inside the liquid rocket;
a second acquisition unit configured to acquire a target operation parameter corresponding to the actual operation parameter;
a determination unit for determining a target fuel flow rate or a target oxygen flow resistance of the liquid rocket by a PI control method based on the target operation parameter and the actual operation parameter;
and the adjusting unit is used for adjusting the opening of the fuel regulating valve according to the target fuel flow, or adjusting the opening of the oxygen auxiliary regulating valve according to the target oxygen flow, or adjusting the opening of the oxygen main regulating valve according to the target oxygen resistance.
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| CN202111585983.6A CN114165360A (en) | 2021-12-17 | 2021-12-17 | Method and device for adjusting thrust of liquid rocket |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111585983.6A CN114165360A (en) | 2021-12-17 | 2021-12-17 | Method and device for adjusting thrust of liquid rocket |
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| CN111692014A (en) * | 2020-06-18 | 2020-09-22 | 安徽九州云箭航天技术有限公司 | Liquid rocket engine, thrust control method and device thereof and carrier rocket |
| CN112377330A (en) * | 2021-01-18 | 2021-02-19 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket engine thrust adjusting method, device, equipment and storage medium |
| CN112948644A (en) * | 2019-12-10 | 2021-06-11 | 北京亿华通科技股份有限公司 | Valve opening control method and device, computer equipment and storage medium |
| CN113090413A (en) * | 2021-05-12 | 2021-07-09 | 北京星际荣耀空间科技股份有限公司 | Open type variable thrust rocket engine, rocket and control method |
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| CN112948644A (en) * | 2019-12-10 | 2021-06-11 | 北京亿华通科技股份有限公司 | Valve opening control method and device, computer equipment and storage medium |
| CN111692014A (en) * | 2020-06-18 | 2020-09-22 | 安徽九州云箭航天技术有限公司 | Liquid rocket engine, thrust control method and device thereof and carrier rocket |
| CN112377330A (en) * | 2021-01-18 | 2021-02-19 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket engine thrust adjusting method, device, equipment and storage medium |
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